Aeroplane



'March 22 ,2 1927.

C. H. TAYLOR ET Al.

AEROPLANE Filed oct. 151921 '7 sheets-sheet 1 al az/ az y i jazz al! @10 a9 Q g l 19M/SMM@ @j fan/dw ATTORNEY.` I

'March 22 1927.

c. H. TAYLOR ET AL EROPLANE Filed Qct. 15. 1921 7Sheets-Sheet 5 1574 2 @uw C8 IDMMATQRNEY.

March 22, 1927. 1,622,242

C. H. TAYLOR ET AL AEROPLANE v' sheets-sheet l 5 Filed Oct. l5. 1921 Q'MMTTvoREY. I

- 1,622,242 c. H. TAYLOR ET AL AEROPLANE March 22, 1927.-

Fledoct. 15. 1921 7 sheets-sheet 6 w (fi wvamlow WW di.

March 22, 1927.

C. H. TAYLOR ET AL AEROPLANE Filed oct. 15. 1921 7 sheets-sheet v NQQUS@ lvide a lightz strong,

Patented Mar. 22," 1927.

UNITED "STATES PA'TEN T oFFlcE.

'CECIL HAMELIN TA-YLOR AND BOUEWIJN B. NEUTEBOOM, 0F DETROIT, MICHIGAN.

.AEROPLANE Applfeauon mea october 15, 1921. serial in. 507,848.

`relates to aeroplanes and a our improvements is to pro.- metal Jconstruction that will be easilyassembled. In the accompanying drawings, Figure 1 is'a side elevation of an aeroplane embodying our invention. 1 Fig. 2 is a section on the line II--II' Fi 1.

i 3 is a detailedectional view on-the' line `II--III Fig. 2.

Fig. 4 is a detailed sectional ViewY illustrating the mode of attachingfthe wings to the body.

Fig. 5 is a detailed sectinal view in the plane V-V Fig. 4

Fig. 6 is a plan view of the rear portion of the aeroplane.

Fig. 7 is a detailed VII-TVH Fig. 6.

Fig. 8 is a detailed section on the line viii-VIII Fig. 1. A f

Fig. 9 is a'view similar to Figa). 8 showing` a modified construction.

. Fig. 10 is a perspective view of one of the seotionsgof which the body-oi the plane is composed. f b'lg. 11 is a `front view ofthe aeroplane, the propeller and 'the cover a being re-` moved to show the inner construction.

Fig. 12 is a detailed perspective view showing' the construction for supporting the engine.y w

Fig. 13 is a perspective view partly in seotiofn of the portion of the aeroplaneI to-tlie sectional plane XIII-XIII Fig. 1. Fig.l 14 is a perspective view of the filling piece at the rear end f the .body of the aeroplane.

15 isa perspective view of the rear end of the body of the aeroplane, the finishng cap an" being removed and also the ruders. f-

Our invention special object of section on the line Fig. 16 is a perspective view of an end portion of one of the ribs of the wing illustrating the mode of securing lthe wlng to the..

Fig. 17 is a cross section of the wing. Fig. 18 is a detailed sectional view of a portion of the wing shown .in Fig'l ina plane at right angles to that of said figure. Fig. 19 is a detailed sectional view illustrating the mode of ttaching the ribs to 'the d'eck'of' the 4' j 20 'is a p an view'of the wing and Lof Fig. 20.

-Jacent sections as indicated adjacent portion ofthe body, partly broken away to exhibit the interior construction. i

. Fig. 21 is a view similar to Fig. 20, the section being taken at right angles to that Fig 22 is a detailed section on the line XXII-XXII Fig. 6

a is the body or fuselage of the plane.

'This is made up of annular or elliptical seotions indicated in Fig. 1 bytheY reference characters a2 lto au. At the rear of the plane is a cap or finishing piece L12-and at the front of the body of the sections al?, a, a and i1a which are chamthe admission and withdrawal of the engine. This opening is covered by a suitably formed cada. The sections of which the body is com-- posed are of thinsheet aluminum amd are formed into the approximate shape of cylinders with their end edges turned inward to form flanges as my, a* in Fi 10. These sections are placed together en for end with the deck being I plane are part fered ofi' as indicated to leave an opening for the anges corresponding'to ay contiguous of the body and adjacent a rod jn is passed apertures 1n sald b being screwed7 There are a series of wires w that pass thru aperturesin the fianges of the sections secured at the rear of the cap piece al and at the forward end tothe foremost available part of the aeroplane and tensioned by secu/1"- ing means to hold the various sections together.v

' At the forward portion of the body where thestrain of landing, ing fli ht, must be sustained b the body, strengt ening lat annular or elliptical rings .a as are placed between the anges ofaddistinctly in Fig. 4. The Han esroi'l the sections are then bound ti htly to t i Te rings a toward the/front of the bo y and where the engine/is located, areprovided with lugs w02 (Figs. 11 and 12) to serve as means for securing the engine to the bod of the plane. l

Tbward the/rear end of the body it is and supporting durthe portion of the body i m are placed over e anges ese strengthening ribs or rin u i desirable to providefins c, c and 3 (Fig. 1 5),

as the case may be,

therefore. ,the annularl section construction is replaced in this locality by a construction that substitutes quadrants or plates formed like the sections of the body but extending only a quarter way around the circle, their ends beingkturnedoutward to contribute to the forming of the fins. This construction is well illustrated in Figs. 6, 7 and 15. The flanges of these quadrant plates at their ends are bound together and at their outer edges at the ridge of the fins are secured together by the constructionshown in Figs 8, 9 and 13, this joint construction also extending to the cockpit of the body. This joint. construction is described as follows:

Two plates ff having their lower edges bent outward at f? are interposed between adjacent edges of the ring or quarter ring, their bent portions f2 extending and engaging undery the flanges ay at the edges of the section or quarter section. The edges of said section or quarter `section to be bound together form flanges engaging on opposite sides of the plates ff as shown distinctly in Figs. 8 and 9., A bindingpiece g, having the cross section of an inverted U, is then placed over the upper edges of the plates ftf and the contiguous flanges of the arts o the body section and the whole is ound together by a bolt g2 passing through apertures in said flanges as shown in Fig. 8 or by indenting the side flanges of the inverted U piece g as shown in Fig. 9.

(Fig. 14) is a ring adapted tofit in the rear end of the body of the plane to form a finishing piece. This ring is provided with half bearings h* extending radi'- ally to receive the shafts of the rudders or aerofoils. A cap a12 is then placed over the rear end of the 4body having bearing ortions corresponding to h* and secure in lace, thus formin the finishing of the rear end of the body o the lane.

b indicates the wingo the plane. This is forred with a cover part?)3 and a spacing means serving both for bracing and to constitute a girder-like construction to prevent the bending of the plane longitudinally as indicated by the broken -line in Fig. 21. This spacing means consists' of thin sheet metal secured to the upper and lower decks of the plane as indicated at b5 and b in Fig. 17 and extending slantingly from one plane to the other, the various parts forming a substantially continuous corrugated surface transversely of the plane the plane surfaces each substantially in a single plane extending longitudinally of the wing. Adjacent portions of these spacing and strengthening means b2 of the wing are bent or warped inward at their ends as illustrated in Fig. 16 to form attaching flanges bT bl which engage on opposite sides of rings am said sections, sai

and are bolted thereto. be strengthened by fish-platesas shown. The middle of the spacing and strengthening means b? is cut away as indicated at b* to lighten the construction while retaining the strengthening function of the part b. c2 e2 are landing wheels connected to the body by the struts or frame members e e. e3 `ig. 3). is a strengthening frame placed between the flanges n.33/ of the sectionaB and secured by bolts passing through such flanges and also through the rings aa'. This frame consists of side pieces c* e* and a bottom `plate er. The side pieces c4 are turned outward at. their ends to forni securing flanges eT c7- (Fig. 2) through which the rivets or bolts passing through the rings am and the flanges azy, aag/ and a-"y pass. outer wall of the bodya is cut away to permit a securing bolt c to pass therethrough which serves to connect one of the braces or frame ieces e with the bottom of the strengthenmg frame e3.

)Vhat we claim is:

1. An air craft body composed of annular sections of thin metal, said sections having their yedges turned inward, said sections being secured together axially in line with each other, a strengthening ring interposed between adjacent edges of said sections and stress transmitting parts secured to said rings.

2. An aircraft body composed of annular sections secured together axially in line with each other, said sections being turned at right angles curing flanges, one rod or more extending These flanges should at their edges to form se` through saidv flanges and means whereby y said rod 1s caused to bind said sections to gether.

3. An aircraft bodycomposed of'annular sections of thin metal, said sections having their edges turned inward, said sections being secured together axially in line with each other by binding the in-turned edges of adjacent sections together, and strengthening rings bound between said flanges where especially violent strains occur. 4. In an aeroplane body, the combination of annular sections placed axially in line and strengthenin rings interposedbetween sectlons being turned inward at their edges to form flanges in planes at right angles to vtheir surfaces, said rings being interposed between adjacent flanges of said sections where especially violent strains occur and means flanges-and ring together.

5. In an aeroplane body, the combination of annular sections placed axially in line and strengthening rings interposed between said sections, and a wing construction secured to said rings.

6. In an aeroplane body the combination of annular sect1ons placed axially in line for binding saidI and strengthenin rings interposed between said sections, and landingl gear-secured to said rings.

, 7. In an aeroplane body, the combination of annular sections placed axiall in line and strengthening rings interposed etween said sections, a strengthening frame extending between adjacent pairsof said rings and a landing gear secured to said strengthening frame.

8. In an aeroplane body the combination' in' line rings of annular sections laced axially with each other, an strengthemn interposed between said sections, an an engine secured to said' rings.

9. The body construction fo aircraftprovided with/fins, plates adapte to form the and secured thereto by indenting the side turned at theirwalls of said securing piece so as to force the material into apertures in said flanges. 30' v '11.5 An aircraft having its walls niade of sheet metal having adjacent edges vturned outward to form securing flanges, having. end edges'turned inward to form other se` curing flanges, first mentioned anges and engaging under the last named flanges anda securing strippassing over ,the first named flanges andsecuring the .same togethers() as to secure said plates bet-Weenv said llanges.

12. Anlaircraft having its walls made of 4sheet metal having adjacent edges turned outward to form securing flanges, having endl edges turned inward to form other securing flanges, plates placed between the first 'mentioned flanges-and engaging under `the last named flanges. 13. An aeroplane body 'havin :half bearings at its rear end and a cap aving oor-l responding half vbearings at its -inner end fitting over and secured to the said rear end of the body. In testimony whereof, we sign lthis specification.

n lCEGID HAMELIN TAYLOR. BOUDEWIJN B. NEUTEBOOM.

lates placed between theji 

